EP0675334B1 - Aerodynamic stabilisation and braking device for air-drop body - Google Patents
Aerodynamic stabilisation and braking device for air-drop body Download PDFInfo
- Publication number
- EP0675334B1 EP0675334B1 EP19950400414 EP95400414A EP0675334B1 EP 0675334 B1 EP0675334 B1 EP 0675334B1 EP 19950400414 EP19950400414 EP 19950400414 EP 95400414 A EP95400414 A EP 95400414A EP 0675334 B1 EP0675334 B1 EP 0675334B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flaps
- missile
- dynamic pressure
- flap
- designed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
- F42B10/16—Wrap-around fins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
- F42B10/50—Brake flaps, e.g. inflatable
Definitions
- the present invention relates to dropable vehicles from an aircraft, of the type fitted with passive stabilization means aerodynamics, such as fins, intended for take an initial trajectory after dropping substantially parallel to the speed of the aircraft.
- aerodynamics such as fins
- aircraft must be interpreted as covering both devices to rotary wing as those with fixed wing.
- the invention finds an important application in the field of infrared or electromagnetic decoys which, to be effective, begin to play their role nearby of the aircraft to cause the hang of a self-steering or radar of a hostile and then have to move away sufficiently progressive that the self-director or the radar stays on them, but fast enough so that a missile self-director or a radar cannot, after extinguishing the lure, hang on again the aircraft.
- CH-A-480 612 which corresponds to the preamble of claim 1
- a rocket having brake flaps deployable from a position where they are pressed against the body at a stop position, substantially perpendicular to the body.
- the shape and inclination of flaps remain unchanged regardless of the train, due that the flaps bear against a stop or are put in place by a drawer.
- DE-A-2 637 793 a dispersion munition provided with elastic lamellae, intended to bring the ammunition in a vertical position.
- the slats deploy as soon as the ammunition is out of its container and take an orientation of minus 10 °, typically around 20 °.
- the constitution of these slats gives them an effect that is not what you are looking for for the invention.
- the present invention aims in particular to provide a machine whose spacing law after release from an aircraft is almost insensitive to flight conditions, unlike previously known devices.
- the invention proposes for this purpose a machine according to the characterizing part of the claim 1.
- the machine whose general appearance is shown in Figures 1 to 3, is intended to be used as an infrared lure or electromagnetic. It has a body 10, of general appearance cylindrical, having a front cone and a boundary envelope a chamber 12 which contains the payload: a load pyrotechnic or a jammer as appropriate.
- the craft is designed to be placed in a magazine cell and for be evicted on demand by a charge of unloading represented.
- the charger itself may have a constitution known, for example that described in the patent application No. 93 10928 of the applicant (FR-A-2 710 025).
- the body carries aerodynamic stabilization means of the machine, intended to orient its longitudinal axis along of the trajectory.
- These purely passive means are formed by several fins or fins 14. These fins, four in number in the illustrated embodiment, are each fixed to two sockets 16 rotating on two aligned axes arranged in the body.
- Pre-compressed means tend to move the fins 14 from their folded position and bring them in the radial orientation where they are shown in Figures 1 and 2 and dashed in Figure 3.
- These means can be constituted by springs (not shown).
- the final orientation of the fins is fixed by support of these fins against a stop of the envelope.
- the machine further comprises flaps which can be deployed automatically after release.
- each of these flaps 17, four in number is constituted by a spring steel plate, the front part of which is held pressed against the body by fixing means, such as screws 18.
- the flaps 17 are kept applied against the body of the machine, under the fins 14, and are therefore compact. They are preformed in the deployed position, so that they are then under tension and in the absence of stress they take a free position making a determined angle a with the axis of the machine ( a ⁇ 45 ° for example).
- the elasticity of the flaps is such that the dynamic pressure exerted on them in flight gives them an angle relative to the axis of the body which depends directly on the dynamic pressure and which is less than a .
- the length of the flaps 17 and the fins 14 is such that they do not project beyond the rear of the body.
- each flap 17 is reinforced by shorter elastic blades 20 whose presence modifies the law of deformation. These additional blades will be or not present according to the law of variation of the drag at give to the craft. They are fixed flat on the shutters, for example by rivets 22.
- FIG 3 shows that the addition of the flaps of aerodynamic braking does not imply a decrease in payload of decoy and modifies very little the outer geometry of the machine.
- the bulges that represent the sockets needed to articulate the fins 14 and allow them to fold over the flaps take place easily, in the cells, square in shape, of the charger. It will simply be necessary, in general, to give each of the flaps 17 a width less than the body diameter, as shown in Figure 3.
- the overall dimensions extra due to the fins is shown in the figure 3 by a dashed frame. Deployment of the fins, such as indicated by the arrow f, releases the flaps 17 and allows them to deploy in turn.
- the shape of the fins 14 and that of the flaps 17, as well that the nature of the flap fixing means depend on of the intended application. We can indicate as an example that in the case of a device consisting of a lure with a gauge of 30 mm and about twenty centimeters long, four flaps without reinforcing blades, spring steel 0.6 mm thick, fixed to the body by a few solder points.
- each flap 17a is constituted by an elastic metal blade (spring steel in general), articulated on the body to the back of the skates.
- each flap 17a can be welded to one of the elements of a hinge 24 placed immediately behind the rear sockets 16.
- the hinges have a limited clearance, so that the flap in the free state, once turned towards the rear , make an angle b of about 45 ° with the axis of the body, near the hinge.
- the flap 17a is intended to be folded towards the nose of the machine when it is stored and kept pressed against the body by a fin 14 ( Figure 4).
- the shutter can be preformed to take the form shown in solid lines in FIG. 5 as soon as the machine is ejected and the fins 14.
- the flaps 17a have a raised beak 26
- their deployment is caused by the action of the wind on beak.
- the wind action can be replaced or supplemented by that of other means, for example by a pincer spring mounted on the hinge 24, a spring intended to take off slightly the flap of the body when released, or a wire of traction connected to the corresponding fin.
- the flaps 17a take a form which depends on the dynamic pressure acting on them, intermediate between the form indicated in dashed lines and the form indicated in dashes in figure 5. If necessary, the hinge 24 can be fitted with a retractable or destructible stop under a given constraint, so as to release the shutter beyond a given dynamic pressure and to reduce then maximum drag.
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Description
La présente invention concerne les engins largables depuis un aéronef, du type muni de moyens passifs de stabilisation aérodynamique, tels que des ailettes, destinés à prendre une trajectoire initiale après largage sensiblement parallèle à la vitesse de l'aéronef. Le terme "aéronef" doit être interprété comme couvrant aussi bien les appareils à voilure tournante que ceux à voilure fixe.The present invention relates to dropable vehicles from an aircraft, of the type fitted with passive stabilization means aerodynamics, such as fins, intended for take an initial trajectory after dropping substantially parallel to the speed of the aircraft. The term "aircraft" must be interpreted as covering both devices to rotary wing as those with fixed wing.
L'invention trouve une application importante dans le domaine des leurres infrarouges ou électromagnétiques qui, pour être efficaces, commencent à jouer leur rôle à proximité de l'aéronef pour provoquer l'accrochage d'un auto-directeur ou d'un radar d'un hostile, puis doivent ensuite s'éloigner de façon suffisamment progressive pour que l'auto-directeur ou le radar reste accroché sur eux, mais suffisamment rapide pour qu'un auto-directeur de missile ou un radar ne puisse, après extinction du leurre, s'accrocher de nouveau sur l'aéronef.The invention finds an important application in the field of infrared or electromagnetic decoys which, to be effective, begin to play their role nearby of the aircraft to cause the hang of a self-steering or radar of a hostile and then have to move away sufficiently progressive that the self-director or the radar stays on them, but fast enough so that a missile self-director or a radar cannot, after extinguishing the lure, hang on again the aircraft.
On connaít déjà (CH-A-480 612 qui correspond au préambule de la revendication 1) une roquette ayant des
volets de freinage déployables d'une position où ils sont
plaqués contre le corps à une position de butée, sensiblement
perpendiculaire au corps. La forme et l'inclinaison des
volets restent inchangées quelle que soit la traínée, du fait
que les volets prennent appui contre une butée ou sont mis
en place par un tiroir. On connaít également (DE-A-2 637 793)
une munition à dispersion munie de lamelles élastiques,
destinées à amener la munition en position verticale. Pour
cela, les lamelles se déploient dès que la munition est
sortie de son conteneur et prennent une orientation d'au
moins 10°, typiquement d'environ 20°. La constitution de ces
lamelles leur donne un effet qui n'est pas celui recherché
pour l'invention. We already know (CH-A-480 612 which corresponds to the preamble of claim 1) a rocket having
brake flaps deployable from a position where they are
pressed against the body at a stop position, substantially
perpendicular to the body. The shape and inclination of
flaps remain unchanged regardless of the train, due
that the flaps bear against a stop or are put
in place by a drawer. We also know (DE-A-2 637 793)
a dispersion munition provided with elastic lamellae,
intended to bring the ammunition in a vertical position. For
this, the slats deploy as soon as the ammunition is
out of its container and take an orientation of
Les leurres actuels, qu'ils soient équipés ou non d'une charge de propulsion, ne permettent pas de remplir cette condition dans toute l'enveloppe de vol des avions à équiperCurrent lures, whether or not equipped with a propellant charge, do not fill this condition throughout the flight envelope of the aircraft to be equipped
Si par exemple on donne à un leurre non propulsé, stabilisé aérodynamiquement, un coefficient de trainée Cx tel qu'il procure à l'engin une séparation par rapport à l'avion satisfaisante à forte vitesse et basse altitude, ce coefficient ne pourra procurer de séparation suffisante pour une éjection à vitesse inférieure ou altitude supérieure, du fait de la chute de la pression dynamique.If for example we give to a non-powered lure, aerodynamically stabilized, a drag coefficient Cx such that it gives the machine a separation from the plane satisfactory at high speed and low altitude, this coefficient cannot provide sufficient separation for a ejection at lower speed or higher altitude, due to from the drop in dynamic pressure.
La présente invention vise notamment à fournir un engin dont la loi d'écartement après largage depuis un aéronef est quasiment insensible aux conditions de vol, contrairement aux engins antérieurement connus. L'invention propose dans ce but un engin suivant la partie caractérisante de la revendication 1.The present invention aims in particular to provide a machine whose spacing law after release from an aircraft is almost insensitive to flight conditions, unlike previously known devices. The invention proposes for this purpose a machine according to the characterizing part of the claim 1.
D'autres caractéristiques et des modes particuliers de réalisation sont définis dans les sous-revendications.Other characteristics and particular modes of realization are defined in the subclaims.
On peut ainsi adapter la traínée de l'engin aux conditions d'éjection, de façon que la trajectoire relative de l'aéronef et de l'engin respecte un gabarit déterminé, quelles que soient ces conditions, au moins dans un domaine d'utilisation prédéterminé.We can thus adapt the drag of the machine to the conditions ejection, so that the relative trajectory of the aircraft and the craft respect a given size, whatever these conditions, at least in one area of predetermined use.
Il sera surtout question par la suite du cas d'un engin, tel qu'un leurre, démuni de propulseur. Mais l'invention s'applique également au cas d'un engin muni d'une charge de propulsion propre, donnant une poussée non ajustable, destinée soit à amener l'engin à l'avant de l'aéronef après largage, soit à ralentir l'accroissement du retard pris par l'engin.It will be mainly a question afterwards of the case of a machine, such as a lure, without propellant. But the invention also applies in the case of a machine fitted with a load of clean propulsion, giving a non-adjustable thrust, intended either to bring the machine to the front of the aircraft after drop, or to slow the increase in delay the craft.
Dans tous les cas, le maintien de la loi de séparation dans un gabarit prédéterminé s'effectue sans intervention extérieure, sans réglage préliminaire, sans moyens actifs à bord de l'engin.In all cases, the maintenance of the law of separation in a predetermined template is carried out without intervention external, without preliminary adjustment, without active means to edge of the craft.
Les dispositions ci-dessus, ainsi que d'autres utilisables avantageusement en liaison avec les précédentes, mais pouvant l'être indépendamment, apparaítront mieux à la lecture de la description qui suit de modes particuliers de réalisation, donnés à titre d'exemples non limitatifs.The above provisions, as well as other usable advantageously in conjunction with the previous ones, but can be independently, will appear better at reading the following description of particular modes of embodiment, given by way of nonlimiting examples.
La description se réfère aux dessins qui l'accompagnent, dans lesquels :
- la figure 1 montre les éléments concernés par l'invention d'un dispositif constituant un premier mode de réalisation, vu en demi-élévation avec coupe partielle, alors que les volets sont repliés ;
- la figure 2, similaire à la figure 1, montre les volets totalement déployés ;
- la figure 3 est une vue en coupe suivant la ligne III - III de la figure 2 ;
- les figures 4 et 5, similaires à la fig. 1, montrent un autre mode de réalisation, les volets étant représentés à l'état replié (figure 4) et à l'état déployé (figure 5).
- Figure 1 shows the elements affected by the invention of a device constituting a first embodiment, seen in half-elevation with partial section, while the flaps are folded;
- Figure 2, similar to Figure 1, shows the flaps fully deployed;
- Figure 3 is a sectional view along line III - III of Figure 2;
- Figures 4 and 5, similar to fig. 1, show another embodiment, the flaps being shown in the folded state (FIG. 4) and in the deployed state (FIG. 5).
L'engin dont l'aspect général est montré en figures 1 à
3, est destiné à être utilisé comme leurre infrarouge ou
électromagnétique. Il comporte un corps 10, d'allure générale
cylindrique, ayant un cône avant et une enveloppe délimitant
une chambre 12 qui contient la charge utile : une charge
pyrotechnique ou bien un brouilleur selon le cas. L'engin est
prévu pour être placé dans un alvéole de chargeur et pour
être expulsé à la demande par une charge de dépotage non
représentée. Le chargeur lui-même peut avoir une constitution
connue, par exemple celle décrite dans la demande de brevet
n° 93 10928 de la demanderesse (FR-A-2 710 025).The machine whose general appearance is shown in Figures 1 to
3, is intended to be used as an infrared lure or
electromagnetic. It has a
Le corps porte des moyens de stabilisation aérodynamique
de l'engin, destinés à orienter son axe longitudinal le long
de la trajectoire. Ces moyens, purement passifs, sont
constitués par plusieurs ailettes ou ailerons 14. Ces ailettes,
au nombre de quatre dans le mode de réalisation illustré,
sont fixées chacune à deux douilles 16 tournant sur deux
axes alignés ménagés dans le corps. Des moyens précomprimés
tendent à écarter les ailettes 14 de leur position repliée
et à les amener dans l'orientation radiale où elles sont
montrées en figures 1 et 2 et en tirets sur la figure 3. Ces
moyens peuvent être constitués par des ressorts (non représentés).
L'orientation finale des ailettes est fixée par
appui de ces ailettes contre une butée de l'enveloppe.The body carries aerodynamic stabilization means
of the machine, intended to orient its longitudinal axis along
of the trajectory. These purely passive means are
formed by several fins or
Conformément à l'invention, l'engin comporte de plus des
volets déployables automatiquement après largage. Dans le cas
illustré sur les figures 1 à 3, chacun de ces volets 17, au
nombre de quatre, est constitué par une plaque en acier à
ressort dont la partie avant est maintenue plaquée le long
du corps par des moyens de fixation, tels que des vis 18.
Lorsque l'engin est stocké, les volets 17 sont maintenus
appliqués contre le corps de l'engin, sous les ailettes 14,
et sont donc peu encombrants. Ils sont préformés en position
déployée, de façon à être alors sous tension et qu'en l'absence
de contrainte ils prennent une position libre faisant
un angle déterminé a avec l'axe de l'engin (a ≈ 45° par
exemple). L'élasticité des volets est telle que la pression
dynamique qui s'exerce sur eux en vol leur donne un angle par
rapport à l'axe du corps qui dépend directement de la
pression dynamique et qui est inférieur à a. La longueur des
volets 17 et des ailettes 14 est telle qu'ils ne débordent
pas à l'arrière du corps.According to the invention, the machine further comprises flaps which can be deployed automatically after release. In the case illustrated in FIGS. 1 to 3, each of these
Dans le mode de réalisation illustré sur les figures 1
et 2, la partie avant de chaque volet 17 est renforcée par
des lames élastiques plus courtes 20 dont la présence modifie
la loi de déformation. Ces lames supplémentaires seront ou
non présentes suivant la loi de variation de la traínée à
donner à l'engin. Elles sont fixées à plat sur les volets,
par exemple par des rivets 22.In the embodiment illustrated in Figures 1
and 2, the front part of each
La figure 3 montre que l'adjonction des volets de
freinage aérodynamique n'implique pas une diminution de la
charge utile de leurrage et ne modifie que très peu la
géométrie extérieure de l'engin. Les renflements que représentent
les douilles nécessaires pour articuler les ailettes
14 et leur permettre de se replier au-dessus des volets
prennent place aisément, dans les alvéoles, de forme carrée,
du chargeur. Il sera simplement nécessaire, en général, de
donner à chacun des volets 17 une largeur inférieure au
diamètre du corps, comme le montre la figure 3. L'encombrement
supplémentaire dû aux ailettes est montré sur la figure
3 par un cadre en tirets. Le déploiement des ailettes, comme
indiqué par la flèche f, libère les volets 17 et leur permet
de se déployer à leur tour.Figure 3 shows that the addition of the flaps of
aerodynamic braking does not imply a decrease in
payload of decoy and modifies very little the
outer geometry of the machine. The bulges that represent
the sockets needed to articulate the
La forme des ailettes 14 et celle des volets 17, ainsi
que la nature des moyens de fixation des volets, dépendent
de l'application envisagée. On peut indiquer à titre d'exemple
qu'il suffit, dans le cas d'un engin constitué par un
leurre ayant un calibre de 30 mm et une vingtaine de centimètres
de long, de quatre volets démunis de lames de renfort,
en acier à ressort de 0,6 mm d'épaisseur, fixés sur le corps
par quelques points de soudure.The shape of the
Le mode de réalisation montré en figures 4 et 5, où les
éléments déjà représentés sur les figures 1 à 3 portent le
même numéro de référence, comporte encore des ailettes de
stabilisation 14 et des volets déployables 17a.The embodiment shown in Figures 4 and 5, where the
elements already shown in Figures 1 to 3 bear the
same reference number, still has fins of
Les ailettes de stabilisation ont la même forme et le
même montage que dans le cas des figures 1 à 3. En revanche,
chaque volet 17a est constitué d'une lame en métal élastique
(acier à ressort en général), articulée sur le corps à
l'arrière des patins. Pour cela chaque volet 17a peut être
soudé sur un des éléments d'une charnière 24 placée immédiatement
derrière les douilles arrière 16. Les charnières
ont un débattement limité, de façon que le volet à l'état
libre, une fois tourné vers l'arrière, fasse un angle b
d'environ 45° avec l'axe du corps, à proximité de la charnière.The stabilization fins have the same shape and the same mounting as in the case of FIGS. 1 to 3. On the other hand, each
Le volet 17a est prévu pour être replié vers le nez de
l'engin lorsqu'il est stocké et être maintenu en appui contre
le corps par une ailette 14 (figure 4). Le volet peut être
préformé de façon à prendre la forme montrée en traits pleins
sur la figure 5 dès éjection de l'engin et déploiement des
ailettes 14. Lorsque les volets 17a présentent un bec relevé
26, leur déploiement est provoqué par l'action du vent sur
le bec. L'action du vent peut être remplacée ou complétée par
celle d'autres moyens, par exemple par un ressort à pincette
monté sur la charnière 24, un ressort destiné à décoller
légèrement le volet du corps lorsqu'il est libéré, ou un fil
de traction relié à l'ailette correspondante.The
Une fois déployés, les volets 17a prennent une forme qui
dépend de la pression dynamique qui agit sur eux, intermédiaire
entre la forme indiquée en traits mixtes et la forme
indiquée en tirets sur la figure 5. Si nécessaire, la charnière
24 peut être munie d'une butée escamotable ou destructible
sous une contrainte déterminée, de façon à libérer le
volet au-delà d'une pression dynamique donnée et à réduire
alors au maximum la traínée.Once deployed, the
Claims (10)
- A missile which may be dropped from an aircraft, provided with passive aerodynamic stabilisation means, designed to follow an initial substantially parallel trajectory at the speed of the aircraft after being dropped, comprising, at the rear, braking flaps (17, 17a) which can be automatically deployed after dropping, characterised in that the flaps are so designed and mounted on the missile body that they assume an orientation directed towards the rear on dropping, such that the dynamic pressure exerted on the flaps automatically modifies the inclination or shape of the flaps in a direction such that the additional drag imparted by the flaps varies as an inverse function of said dynamic pressure, ensuring automatic adaptation to the flight conditions.
- A missile as claimed in claim 1, characterised in that the flaps (17, 17a) are of a flexibility such that they deform immediately they reach their deployed position in a direction which reduces the drag coefficient when the dynamic pressure exerted on them increases.
- A missile as claimed in claim 2, characterised in that the front of said flaps (17) is fixed flat against the body (10) of the missile.
- A missile as claimed in claim 2 or 3, characterised in that the front part of the flaps is reinforced by shorter blades (20) fixed flat against the flaps (17).
- A missile as claimed in claim 2, 3 or 4, characterised in that the flaps are preformed so as to be oriented at approximately 45° relative to the axis of the missile in the released state.
- A missile as claimed in claim 1, characterised in that the flaps are joined to the body of the missile by resilient means which bend under the action of the force exerted on the flaps, in a direction which reduces the drag coefficient when the dynamic pressure increases.
- A missile as claimed in claim 1, characterised in that each flap (17a) is made from a blade of resilient metal, the rear of which is hinge-mounted on the body to the rear of pads by means having a restricted displacement, the flap being designed so that it can be folded in towards the nose of the missile when it is stowed and held supported against the body.
- A missile as claimed in claim 7, characterised in that said flap (17a) has an upturned nose (26) designed to cause deployment due to the action of the wind on the nose.
- A missile as claimed in claim 7 or 8, characterised by elliptic spring means for detaching the flaps.
- A missile as claimed in claims 7, 8 or 9, characterised in that the hinge means (24) are provided with a stop which is retractable or destructible under a given constraint so as to release the flap above a given dynamic pressure.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9402401A FR2716965B1 (en) | 1994-03-02 | 1994-03-02 | Releasable machine with aerodynamic stabilization and braking. |
FR9402401 | 1994-03-02 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0675334A1 EP0675334A1 (en) | 1995-10-04 |
EP0675334B1 true EP0675334B1 (en) | 2000-04-12 |
Family
ID=9460594
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19950400414 Expired - Lifetime EP0675334B1 (en) | 1994-03-02 | 1995-02-27 | Aerodynamic stabilisation and braking device for air-drop body |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP0675334B1 (en) |
DE (1) | DE69516200T2 (en) |
FR (1) | FR2716965B1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2747464B1 (en) * | 1996-04-16 | 1999-09-17 | Aerospatiale | DEPLOYABLE WING FLYING MACHINE |
HUE030169T2 (en) | 2009-01-09 | 2017-05-29 | Forward Pharma As | Pharmaceutical formulation comprising one or more fumaric acid esters in an erosion matrix |
US8278612B2 (en) * | 2010-07-27 | 2012-10-02 | Raytheon Company | Aerodynamic fin lock for adjustable and deployable fin |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1553980C3 (en) * | 1965-02-18 | 1975-05-22 | Breda Meccanica Bresciana S.P.A., Brescia (Italien) | Device for adjusting the firing range of rocket projectiles |
DE977742C (en) * | 1965-04-14 | 1969-04-30 | Kunststofftechnische Studienge | Flying body with knife-shaped tail wings that can be folded out against the direction of the air |
CH480612A (en) * | 1967-09-06 | 1969-10-31 | Oerlikon Buehrle Ag | Rocket with folding tail and braking device |
DE2154584A1 (en) * | 1971-11-03 | 1973-05-10 | Dynamit Nobel Ag | MISSILE FOR COMBATING UNDERWATER TARGETS |
DE2637793C2 (en) * | 1976-08-21 | 1983-11-17 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Device for reducing airspeed and stabilizing the position of cluster munitions |
-
1994
- 1994-03-02 FR FR9402401A patent/FR2716965B1/en not_active Expired - Fee Related
-
1995
- 1995-02-27 DE DE1995616200 patent/DE69516200T2/en not_active Expired - Lifetime
- 1995-02-27 EP EP19950400414 patent/EP0675334B1/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
DE69516200D1 (en) | 2000-05-18 |
EP0675334A1 (en) | 1995-10-04 |
DE69516200T2 (en) | 2000-11-23 |
FR2716965B1 (en) | 1996-05-03 |
FR2716965A1 (en) | 1995-09-08 |
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